CN103303469B - Device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers - Google Patents

Device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers Download PDF

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Publication number
CN103303469B
CN103303469B CN201310282649.2A CN201310282649A CN103303469B CN 103303469 B CN103303469 B CN 103303469B CN 201310282649 A CN201310282649 A CN 201310282649A CN 103303469 B CN103303469 B CN 103303469B
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trailing edge
wedge
boundary
generation unit
flow
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CN103303469A (en
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李伟鹏
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Shanghai Jiaotong University
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Shanghai Jiaotong University
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    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/10Drag reduction

Abstract

The invention discloses a device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers in the technical field of hypersonic flight vehicles. The device comprises a base flow-dividing wedge and a miniature trailing edge vortex generator, wherein the base flow-dividing wedge in a lean-back wedged structure is arranged at the front end of a shock wave and boundary layer interference region, and the distance, in particular the distance between a trailing edge and a shock wave incidence point, is smaller than or equal to the thickness of three boundary layers; the miniature trailing edge vortex generator is arranged on the upper surface of the trailing edge of the base flow-dividing wedge. According to the device, a dropping vortex structure can be generated on the side edge of the flow-dividing wedge to take away a low-energy fluid of the interference region, and a high-turbulivity shearing layer on the trailing edge serves as a buffer strip. The device can control the flow separation caused by the interference between the shock waves and the boundary layers, realizes separation flow control under the condition of Mach number of 4 to 10, and has the characteristics of simple structure, stable performance and the like.

Description

Control the device that High Mach number shock wave is separated with boundary-layer Interference Flow
Technical field
What the present invention relates to is a kind of in hypersonic aircraft technical field, control the device that is separated with boundary-layer Interference Flow of shock wave, specifically a kind of by-pass type, the device that is separated with boundary-layer Interference Flow with the control High Mach number shock wave of compound vortex producer.
Background technology
Hypersonic aircraft realizes one of military rapid strike, rapid-action strategy equipment, in recent years quite by the concern of domestic and international researchist.Shock wave and boundary-layer disturb the interior stream that is extensively present in high hypersonic aircraft and in outflowing, when aircraft flies at High Mach number, intense shock wave and boundary-layer disturb the large scale flow separation usually causing boundary-layer, supervene stronger additional resistance and pitot loss, turbulence intensity simultaneously after shock wave and coefficient of thermal conductivity increase severely, and there is low-frequency oscillation characteristic, the dynamic aerodynamics/thermal load of bringing out may cause the structural failure of aircraft or the actual effect of thermal protection system.As can be seen here, the flow separation phenomenon that shock wave under High Mach number/boundary-layer interference causes is the potential safety hazard of hypersonic aircraft, be the key factor affecting aircraft entirety and critical component safety thereof, and bring difficulty and challenge to the Material selec-tion of aircraft, Standard and heat protection design.
Vortex generator is a kind of controlled control method delaying or suppress shock wave/boundary-layer Interference Flow and be separated, but under High Mach number (4<M<10), due to the increase of shock strength, traditional vortex generator is difficult to play good control effects, and its major cause is the adverse pressure gradient that whirlpool disturbance that traditional vortex generator produces is difficult to overcome intense shock wave and causes.Therefore the apparatus and method proposing the shock wave/boundary-layer Interference Flow separation under a kind of control High Mach number condition of simple and reliable, easy realization are problem demanding prompt solutions.
Through finding the retrieval of prior art, Chinese patent literature CN201210319468, publication date 2013-01-09, describe a kind of vortex generator for the flow separation decay during allowing fluid flow surface, described vortex generator is configured for neighbouring surface and produces at least two vortexs.But the defect of this technology compared with the present invention is: be not suitable for hypersonic fluid, the structure of its vortex generator can produce stronger drag due to shock wave; The shear layer mixing of vortex generator trailing edge can not be strengthened, be difficult to control preferably the flow analysis phenomenon that shock wave and boundary-layer disturb.
Chinese patent literature CN201110322560, publication date 2012-05-16, describe a kind of wind turbine blade comprising vortex generator, the structure of described vortex generator and be arranged as and have contribution to the aerodynamic characteristics of described blade, described vortex generator comprises platform and extension, and platform is fixed in described depression.But under High Mach number condition, this vortex generator can not produce the disturbance of good whirlpool, the effect controlling Flows and be separated can not be played.
Summary of the invention
The present invention is directed to prior art above shortcomings, a kind of device controlling High Mach number shock wave and be separated with boundary-layer Interference Flow is proposed, hypersonic speed shock wave/boundary-layer can be controlled and disturb the flow separation caused, realize the separated flow control of Mach number under 4 ~ 10 conditions, there is the features such as structure is simple, stable performance.
The present invention is achieved by the following technical solutions, the present invention includes: base portion shunting wedge and trailing edge micropower thermoelectric generator, wherein: base portion shunting wedge is layback wedge structure, be arranged at the front end of shock wave and boundary-layer interference range, the distance of its trailing edge and shock incidence point is less than or equal to the thickness of 3 boundary-layers, and trailing edge micropower thermoelectric generator is arranged at the upper surface of base portion shunting wedge trailing edge.
The front and rear edges height H of described base portion shunting wedge 2, H 1and the condition that width D and length L meet respectively is:
0≤H 2≤ H 1≤ δ; 2H 1≤ D≤5H 1; 4H 1≤ L≤10H 1; Wherein: δ is the thickness of incoming flow boundary-layer.
Described trailing edge micropower thermoelectric generator adopts a vortex generation unit or the arrangement of multiple vortex generation unit to form, wherein: the horizontal maximum height h of each vortex generation unit and axial extreme length l meets: 0≤h≤0.3H 1; 0≤l≤0.5H 1; And can regulate according to concrete trailing edge vortex generator different structure.
The shape of described trailing edge vortex generation unit adopts but is not limited to cylindrical, serration, layback type wedge shape, proclined wedge structure.
The spread pattern of described trailing edge vortex generation unit adopts the axisymmetric mode in center, more preferably axially vertical single multiple mode, double alignment thereof, the double arrangement mode such as staggered.
Technique effect
Relative to traditional vortex generator, the technique effect of the by-pass type that the present invention relates to, compound vortex producer comprises:
1) due to shunt effect, unstable state turbulent structure is formed at the lateral margin of base portion shunting wedge, can periodically and shock wave/boundary-layer disturb the separated vorticcs caused to interact, sweep away the low energy fluid near interference range, increase the degeneration-resistant Compressive Strength of shock wave/boundary-layer interference range;
2) due to the effect of trailing edge vortex generator, after flowing through the trailing edge of shunting wedge, form the turbulent shear layer of three-dimensional, strong mixing, effect that turbulent shear layer plays well " alleviating band ", strong adverse pressure gradient on wall is directly incident on for weakening shock wave, shunt the expansion wave system that wedge trailing edge is formed simultaneously, be conducive to accelerating turbulent shear layer, overcome the momentum after shock wave front poor.
Relative to traditional vortex generator, the present invention has three kinds of advantages:
1) by-pass type, compound vortex producer have stronger shunt effect, enhance the degree of irregularity of turbulent boundary layer and degeneration-resistant Compressive Strength, and the leading edge height that the intensity of shunting action shunts wedge by base portion regulates;
2) large scale of lateral margin formation, the eddy structure of periodic swinging of base portion shunting wedge, be conducive to the low energy fluid taking away interference range;
3) by shunting the combination of wedge and micropower thermoelectric generator, significantly enhancing the turbulence intensity of trailing edge shear layer, anti-interference intensity is strengthened.
Accompanying drawing explanation
Fig. 1 is vortex generator structure schematic diagram in embodiment 1.
Fig. 2 is vortex generator structure schematic diagram in embodiment 2.
Fig. 3 is vortex generator structure schematic diagram in embodiment 3.
Fig. 4 is vortex generator structure schematic diagram in embodiment 4.
Fig. 5 is vortex generator structure schematic diagram in embodiment 5.
Fig. 6 is vortex generator structure schematic diagram in embodiment 6.
Detailed description of the invention
Elaborate to embodiments of the invention below, the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Embodiment 1
As shown in Figure 1, the present embodiment device comprises: base portion shunting wedge 1 and trailing edge micropower thermoelectric generator 2, wherein: the base portion shunting wedge 1 of layback wedge structure is arranged at the front end of shock wave and boundary-layer interference range and distance (specifically shunting wedge trailing edge to shock incidence point distance) is less than or equal to the thickness of 3 boundary-layers, and trailing edge micropower thermoelectric generator 2 is arranged at the trailing edge that base portion shunts wedge 1.
The front and rear edges height H of described base portion shunting wedge 1 2, H 1and width D and length L meet respectively: 0≤H 2≤ H 1≤ δ; 2H 1≤ D≤5H 1; 4H 1≤ L≤10H 1; Wherein: δ is the thickness of incoming flow boundary-layer.
As shown in Figure 1, the trailing edge micropower thermoelectric generator 2 in the present embodiment adopts three vortex generation unit 2 axially vertical, namely along the single arrangement of Z-direction.
Described vortex generation unit 3 adopts cylindrical structural, and the horizontal maximum height h of each vortex generation unit 2 and axial extreme length l meets: 0≤h≤0.3H 1; 0≤l≤0.5H 1; And can regulate according to concrete trailing edge vortex generator different structure.
Due to the enhancing of shock strength under High Mach number condition, cause the large scale flow separation producing boundary-layer at shock incidence point annex, utilize the flowing control action of Fig. 1 shown device, the vortex structure produced at lateral margin and the trailing edge of shunting wedge can eliminate flow separation phenomenon, avoids the many counter productives because flow separation causes.
Embodiment 2
As shown in Figure 2, the present embodiment is with the difference of embodiment 1: described trailing edge micropower thermoelectric generator 2 adopts two vortex generation unit 2 axially vertical, namely along the single arrangement of Z-direction; And described vortex generation unit 2 adopts the shape wedge structure that leans forward.
The shape and structure technical requirements details of this vortex generation unit 2 is: the trailing edge height h of described vortex generation unit 2, width d and length l meet respectively: 0≤h≤0.3H 1; H≤d≤2h; H≤l≤3h.
The control effects of the present embodiment under High Mach number condition is similar to embodiment 1.
Embodiment 3
As shown in Figure 3, the present embodiment is with the difference of embodiment 1: described trailing edge micropower thermoelectric generator 2 adopts two vortex generation unit 2 axially vertical, namely along the single arrangement of Z-direction; And described vortex generation unit 2 adopts layback shape wedge structure.
The shape and structure technical requirements details of this vortex generation unit 2 is: the leading edge height h of described vortex generation unit 2, width d and length l meet respectively: 0≤h≤0.3H 1; H≤d≤2h; H≤l≤3h.
The control effects of the present embodiment under High Mach number condition is similar to embodiment 1.
Embodiment 4
As shown in Figure 4, the present embodiment is with the difference of embodiment 1: described trailing edge micropower thermoelectric generator 2 adopts two vortex generation unit 2 axially vertical, namely along the single arrangement of Z-direction; And described vortex generation unit 2 adopts depression broached-tooth design.
The shape and structure technical requirements details of this vortex generation unit 2 is: the trailing edge height h of described vortex generation unit 2, width d and length l meet respectively: 0≤h≤0.3H 1; H≤d≤2h; H≤l≤3h.
The control effects of the present embodiment under High Mach number condition is similar to embodiment 1.
Embodiment 5
As shown in Figure 5, the present embodiment is with the difference of embodiment 1: described trailing edge micropower thermoelectric generator 2 adopts 6 vortex generation unit 2 axially vertical, i.e. the double alignment along Z axis side;
Distance of shaft centers between double vortex generation unit 2 from the parameter request of DX is: l≤DX≤2l.
The present embodiment, compared to embodiment 1, can strengthen the shear layer mixed effect to shunting wedge trailing edge, better suppresses the flow analysis phenomenon that shock wave causes, but may cause the resistance larger compared to embodiment 1.
Embodiment 6
As shown in Figure 6, the present embodiment is with the difference of embodiment 1: described trailing edge micropower thermoelectric generator 2 adopts 5 vortex generation unit 2 axially vertical, namely doublely along Z axis side is staggered;
Distance of shaft centers between double vortex generation unit 2 from the parameter request of DX is: l≤DX≤3l.
The present embodiment, compared to embodiment 1, can strengthen the shear layer mixed effect to shunting wedge trailing edge, better suppresses the flow analysis phenomenon that shock wave causes, but may cause the resistance larger compared to embodiment 1.

Claims (5)

1. one kind for controlling the device that High Mach number shock wave is separated with boundary-layer Interference Flow, it is characterized in that, comprise: base portion shunting wedge and trailing edge micropower thermoelectric generator, wherein: the base portion shunting of layback wedge structure wedges the front end and distance that are placed in shock wave and boundary-layer interference range, namely trailing edge is to the distance of shock incidence point, be less than or equal to the thickness of 3 boundary-layers, trailing edge micropower thermoelectric generator is arranged at the trailing edge of base portion shunting wedge;
The front and rear edges height H of described base portion shunting wedge 2, H 1and the condition that width D and length L meet respectively is: 0≤H 2≤ H 1δ; 2H 1≤ D≤5H 1; 4H 1≤ L≤10H 1; Wherein: δfor the thickness of incoming flow boundary-layer.
2. device according to claim 1, is characterized in that, described trailing edge micropower thermoelectric generator adopts a vortex generation unit or the arrangement of multiple vortex generation unit to form, wherein: the horizontal maximum height of each vortex generation unit hwith axial extreme length lmeet: 0≤ h≤ 0.3H 1; 0≤ l≤ 0.5H 1, wherein: H 1for the trailing edge height of base portion shunting wedge.
3. device according to claim 2, is characterized in that, the shape of described vortex generation unit adopts cylindrical, serration, layback type wedge shape or proclined wedge structure.
4. device according to claim 2, is characterized in that, described arrangement adopts the axisymmetric mode in center.
5. device according to claim 2, is characterized in that, described arrangement adopts axially vertical single multiple mode, axially vertical double alignment thereof or double staggered arrangement mode.
CN201310282649.2A 2013-07-05 2013-07-05 Device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers Expired - Fee Related CN103303469B (en)

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CN106323588A (en) * 2016-10-12 2017-01-11 南京航空航天大学 Device and method for rapid development of boundary layer in supersonic flow field
WO2018129721A1 (en) * 2017-01-13 2018-07-19 深圳市大疆创新科技有限公司 Propeller of aircraft, power set and unmanned aerial vehicle
CN109436421B (en) * 2018-11-06 2021-04-27 方祥杰 Preparation method of overhigh flow dividing device for redried tobacco leaves
CN111120461B (en) * 2020-01-19 2021-09-28 中国人民解放军海军工程大学 Underwater flow excitation cavity noise control device
CN112173082B (en) * 2020-08-25 2021-11-16 中国航天空气动力技术研究院 Micro-vortex generating device with auxiliary control of airflow
CN114148508A (en) * 2021-12-28 2022-03-08 中国航天空气动力技术研究院 Control device for inhibiting boundary layer interference flow separation
CN114590418B (en) * 2022-03-09 2023-10-24 厦门大学 Method and device for suppressing surface pulsation pressure of high-speed aircraft
CN114735203B (en) * 2022-06-13 2022-09-23 中国空气动力研究与发展中心高速空气动力研究所 Noise suppression device for triangular prism-shaped aircraft weapons cabin

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